KR102600872B1 - Torch igniter for a combustor - Google Patents

Abstract

The igniter for the combustor of the turbomachinery includes a fuel inlet in fluid communication with the mixing plenum. A mixing plenum is positioned upstream of the mixing channel. The air inlet is in fluid communication with the mixing plenum and the ignition source is in operative communication with the mixing channel. The igniter may include a mounting flange configured to couple the igniter to the combustor. The ignition source may be positioned proximate the downstream end of the mixing channel and upstream of the mounting flange. The mixing channel may define a venturi shape. The venturi geometry includes a converging section between the upstream end of the mixing channel and the venturi throat.

Description

Torch igniter for combustor {TORCH IGNITER FOR A COMBUSTOR}

The present disclosure generally relates to devices for igniting combustors of turbomachinery.

Gas turbines, aircraft turbines, and various other combustion-based systems include one or more combustors that mix a working fluid, such as air, with fuel and ignite the fuel-air mixture to produce high temperature and high pressure combustion gases. For example, commercial gas turbines can be used for power generation. A typical gas turbine used to generate electric power includes a compressor, combustor, and turbine in series flow order. Ambient air can be supplied to the compressor, and the rotating blades and fixed vanes in the compressor continue to impart kinetic energy to the working fluid (air), producing compressed working fluid in a high energy state. The compressed working fluid exits the compressor, flows through one or more nozzles - where the compressed working fluid mixes with the fuel - and then into the combustion chambers in each combustor - where the mixture is ignited to produce high-temperature and high-pressure combustion gases. It flows. Combustion gases expand within the turbine to produce work. For example, the expansion of combustion gases within a turbine can rotate a shaft connected to a generator, generating electrical power.

Combustion may be initiated by an ignition system in one or more combustors. The ignition system may generate a spark or other ignition source, such as a laser beam or pilot flame, within the combustor.

Because the ignition system is typically located along the side of the combustion chamber, it can emit a spark, beam, or flame into the combustion chamber approximately simultaneously with the fuel-air mixture. The location of the ignition system along the side of the combustion chamber requires penetration through the liner of the combustion chamber, creating turbulence and/or possible sources of leakage through or around the penetration. Additionally, the ignition system located along the side of the combustor interferes with the flow of working fluid between the liner and the fluid sleeve, thereby increasing the pressure difference of the working fluid across the combustion chamber, which reduces the overall efficiency of the gas turbine. . The above configuration may reduce the amount and/or flow rate of working fluid available to mix with fuel in the nozzle. The amount of working fluid available to premix with the fuel directly affects peak flame temperature and NOx emissions.

The ignition system may include an ignition torch. The ignition torch can accommodate fuel flow and air flow. To provide an ignition spark to initiate combustion in the combustion chamber, air and fuel can be mixed in a torch and ignited by an ignition source, such as a spark plug. Spark plugs are typically placed close to the combustion chamber.

Aspects and advantages of the present disclosure may be described in, become apparent from, or be learned through practice of the disclosure.

According to one embodiment, a gas turbine is provided. A gas turbine includes a compressor, a turbine, and a combustor disposed downstream of the compressor and upstream of the turbine. The gas turbine also includes an igniter in operative communication with the combustor. The igniter includes a mixing channel defining a venturi shape. The venturi geometry includes a converging section between the upstream end of the mixing channel and the venturi throat. The igniter also includes a fuel inlet in fluid communication with the mixing plenum. A mixing plenum is positioned upstream of the mixing channel. The igniter also includes an air inlet in fluid communication with the mixing plenum and an ignition source in operative communication with the mixing channel. The ignition source is located downstream of the mixing plenum.

According to another embodiment, an igniter for a combustor of a turbomachinery is provided. The igniter includes a mounting flange configured to couple the igniter to the combustor. The igniter also includes a fuel inlet in fluid communication with the mixing plenum. A mixing plenum is positioned upstream of the mixing channel. The igniter also includes an air inlet in fluid communication with the mixing plenum and an ignition source in operative communication with the mixing channel. The ignition source is positioned proximate the downstream end of the mixing channel and upstream of the mounting flange.

According to another embodiment, an igniter for a combustor of a turbomachinery is provided. The igniter includes a mixing channel defining a venturi shape. The venturi geometry includes a converging section between the upstream end of the mixing channel and the venturi throat. The igniter also includes a fuel inlet in fluid communication with the mixing plenum. A mixing plenum is positioned upstream of the mixing channel. The igniter also includes an air inlet in fluid communication with the mixing plenum and an ignition source in operative communication with the mixing channel. The ignition source is located downstream of the mixing plenum.

Those skilled in the art will, upon reviewing this specification, better understand the features and aspects of the embodiments described above and other features and aspects.

A complete and feasible disclosure of various embodiments, including the best mode of the invention, to those skilled in the art is now set forth in more detail than in the remainder of the specification with reference to the accompanying drawings.
1 is a functional block diagram of an example gas turbine that may include various embodiments of the present disclosure.
2 is a simplified side cross-sectional view of an exemplary combustor that may incorporate one or more embodiments.
3 is a side cross-sectional view of an exemplary igniter according to one or more embodiments of the present disclosure.
Figure 4 is an end view of the exemplary igniter of Figure 3;
Figure 5 is a side cross-sectional view of an exemplary igniter according to one or more embodiments of the present disclosure.
Figure 6 is a side cross-sectional view of an exemplary igniter according to one or more embodiments of the present disclosure.
Figure 7 is a side cross-sectional view of an exemplary igniter according to one or more embodiments of the present disclosure.
Figure 8 is an end view of the exemplary igniter of Figure 7;

Reference will now be made in detail to embodiments of the present disclosure, one or more examples of which are shown in the drawings. The detailed description uses numbers and letters to refer to features in the drawings. Similar or analogous symbols in the drawings and descriptions are used to refer to similar or analogous portions of the present disclosure.

As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish components from each other, and are not intended to indicate the location or importance of individual components. The terms “upstream” and “downstream” refer to the relative direction of fluid flow in the flow path. For example, “upstream” refers to the direction in which the fluid flows, and “downstream” refers to the direction in which the fluid flows. The term “radially” refers to a relative direction approximately perpendicular to the axial centerline of a particular component, and the term “axially” refers to a relative direction approximately parallel and/or coaxial with the axial centerline of a particular component. The term “circumferentially” refers to the relative direction extending around the axial center line of a particular component.

The terminology used herein is intended to describe particular embodiments only and is not intended to be limiting. As used herein, the singular forms are intended to also include the plural forms, unless the context clearly dictates otherwise. The terms “comprise” and/or “comprising” when used herein specify the presence of a referenced feature, entity, step, process, element and/or component, but also specify the presence of another feature, entity, step, process, or component. It will be further understood that this does not preclude the presence or addition of elements, components and/or groups thereof.

Each example is provided to explain the disclosure rather than limit it. In fact, it will be apparent to those skilled in the art that various modifications and variations may be made without departing from the scope or spirit of the disclosure. For example, features illustrated or described as part of one embodiment may be used in another embodiment to form yet another embodiment. Accordingly, the present disclosure includes such modifications and variations as come within the scope of the appended claims and their equivalents.

Although exemplary embodiments of the present disclosure will generally be described for illustrative purposes and with respect to a gas turbine combustor for land-based power generation, those skilled in the art will appreciate that embodiments of the present disclosure are applicable to any style or type of turbomachinery, as claimed in the claims. It will be readily understood that it is not limited to gas turbines for land-based power generation unless specifically cited herein.

Referring now to the drawings, FIG. 1 illustrates a schematic diagram of an exemplary gas turbine 10. The gas turbine 10 generally has an inlet section 12, a compressor 14 disposed downstream of the inlet section 12, at least one combustor 16 disposed downstream of the compressor 14, and a combustor 16. It includes a turbine 18 disposed downstream and an exhaust section 20 disposed downstream of the turbine 18. Additionally, gas turbine 10 may include one or more shafts 22 that couple compressor 14 to turbine 18 .

During operation, air 24 flows through the inlet section 12 to the compressor 14, where the air 24 is continuously compressed to provide compressed air 26 for the combustor 16. At least a portion of the compressed air 26 is mixed with fuel 28 and combusted within the combustor 16 to produce combustion gases 30 . Combustion gases 30 flow from the combustor 16 to the turbine 18, where energy (kinetic and/or heat) is transferred from the combustion gases 30 to the rotor blades (not shown), and thus the shaft ( 22) rotates. The mechanical rotational energy can then be utilized for various purposes, such as driving the combustor 14 and/or producing electrical power. Combustion gases 30 exiting turbine 18 may then be exhausted from gas turbine 10 through exhaust section 20 .

As shown in Figure 2, combustor 16 may be at least partially surrounded by an outer casing 32, such as a compressor discharge casing. The outer casing 32 may at least partially define a high pressure plenum 34 that at least partially surrounds the various components of the combustor 16. High pressure plenum 34 may be in fluid communication with compressor 14 to receive compressed air 26 from compressor 14 (Figure 1). End cover 36 may be coupled to outer casing 32. In certain embodiments, outer casing 32 and end cover 36 may at least partially define the head end volume or portion 38 of combustor 16.

In certain embodiments, head end portion 38 is in fluid communication with high pressure plenum 34 and/or compressor 14. One or more liners or conduits 40 may at least partially define a combustion chamber or combustion zone 42 for combustion of the fuel-air mixture and/or direct combustion gases 30 toward the inlet to the turbine 18. The hot gas path 44 through the combustor may be at least partially defined to allow the hot gases to pass through the combustor. One or more fuel nozzles 50 may be coupled to end cover 36 and extend toward combustion chamber 42 . Igniter 100 may be in operative communication with combustor 16 , and igniter 100 may be configured to initiate combustion in combustor 16 . Igniter 100 may extend axially downstream from end cover 36. The expression “axially” as used herein in relation to the combustor 16 refers to the axial centerline 46 of the combustor 16, e.g., the igniter 100 is positioned along or axially along the axial centerline 46. It may extend downstream from the end cover 36 parallel to the centerline. In other embodiments, igniter 100 may extend at any suitable angle to communicate with combustion chamber 42. For example, in some embodiments igniter 100 may be oriented perpendicular to axial centerline 46.

For example, as shown in FIG. 3 , igniter 100 may include a mounting flange 122 configured to couple igniter 100 to combustor 16 . In some embodiments, mounting flange 122 may include bolt holes 124 that receive bolts to fasten igniter 100 to combustor 16. In particular, mounting flange 122 may be configured to couple igniter 100 to the end cover 36 of combustor 16. In the above-described embodiment, the igniter 100 has an end cover of the combustor 16 such that the central axis 130 of the igniter 100 is substantially parallel to the central axis 46 of the combustor 16 (FIG. 2). It can be coupled to (36).

As can be seen, for example, in FIGS. 3 and 4, the igniter may include one or more air inlets 104. In some embodiments, air inlet 104 may be in fluid communication with head end 38 and is positioned to receive a flow of compressed air 26 from head end 38. In some embodiments, each air inlet 104 opens into a respective air conduit 106. Each air conduit 106 provides fluid communication between a corresponding air inlet 104 and mixing plenum 110. For example, as illustrated in FIG. 3 , fuel conduit 108 may be in fluid communication with mixing plenum 110 through fuel inlet 102 . Mixing plenum 110 may be positioned upstream of mixing channel 112. Fuel 28 and air 26 may be mixed in mixing plenum 110 and mixing channel 112 before being ignited by ignition source 120 . Ignition source 120 may be, for example, a spark plug. Ignition source 120 may be in operative communication with mixing channel 112. In some example embodiments, ignition source 120 may be positioned proximate the downstream end of mixing channel 112. As used herein, terms such as “upstream” or “downstream” refer to the direction of flow of the mixed fuel 28 and compressed air 26 within the igniter 100, e.g., approximately from the mixing plenum 100 to the combustor 16. The direction to the side should be understood, for example the downstream end of mixing channel 112 refers to the end of mixing channel 112 distal from mixing plenum 110 . In some embodiments, ignition source 120 may be positioned upstream of mounting flange 122. Such an embodiment advantageously facilitates access to the ignition source 120 when the ignition source 120 is positioned outside the combustion chamber 16 rather than proximate the combustion chamber 42.

Mixing channel 112 may extend axially between mixing plenum 110 and ejector tube 126. Ejector tube 126 may be positioned downstream of mixing channel 112. In particular, the ejector tube 126 is positioned downstream of the ignition source 120 to receive combustion products, such as hot gases, generated upon ignition of the mixed fuel 28 and air 26 by the ignition source 120. can do. The ejector tube 126 may extend into the combustor 16, for example through the end cover 36, to provide an ignition flame for the combustion chamber 42. In some embodiments, ejector tube 126 may optionally include a swirler 128 downstream of ignition source 120. For example, as illustrated in FIG. 3, the swirler 128 may be a ribbon swirler. Other example embodiments of swirler 128 may include swirler vanes, turbulators, etc.

For example, as illustrated in FIG. 3, the cross-sectional shape of the mixing channel 112 may be constant, for example, the mixing channel 112 may be cylindrical. In other embodiments, mixing channel 112 may have other prismatic shapes, such as mixing channel 112 may be a rectangular prism, or may have other polygonal cross-sectional shapes such as, but not limited to, hexagons.

In some embodiments, mixing channels 112 may define a plurality of distinct inner diameters. Generally, mixing channel 112 may define a first inner diameter portion 114 at an upstream portion of mixing channel 112 and have a minimum inner diameter at a throat portion 116 downstream of first inner diameter portion 114. And the second inner diameter portion 118 can be defined downstream of the throat portion 116. The minimum inner diameter of the throat portion 116 may be smaller than the inner diameter of the first inner diameter portion 114 or the second inner diameter portion 118. In various embodiments, the inner diameter of the first inner diameter portion 114 may be larger than the inner diameter of the second inner diameter portion 118 or may be substantially equal to the inner diameter of the second inner diameter portion 118 . In some embodiments, for example, as illustrated in Figure 5, a plurality of distinct inner diameters may form a venturi shape. As shown in FIG. 5, the first inner diameter portion 114 may form a venturi-shaped converging section 114, the second inner diameter portion 118 may form a diverging section 118, and The throat portion 116 may thus be a venturi throat 116 . In some example embodiments, the venturi shape may include a converging section 114 between the upstream end of mixing channel 112 and venturi throat 116. For example, convergence section 114 may extend between venturi throat 116 and an end of mixing channel 112 proximate mixing plenum 110. The converging section 114 may include a section of mixing channel 112 where the cross-sectional area of mixing channel 114 decreases axially downstream from mixing plenum 110 to venturi throat 116. Accordingly, the venturi throat 116 may define a minimum cross-sectional area of the mixing channel 112 and/or a bending point in the venturi shape. The venturi-shaped diverging section 118 may be positioned downstream of the venturi throat 116. For example, the cross-sectional area of mixing channel 112 may increase axially downstream from venturi throat 116 over the axial length of diverging section 118.

As illustrated in FIGS. 5 and 6 , the fuel inlet 102 is positioned axially (e.g., about the center of the igniter 100) such that fuel 28 is provided at or near the venturi throat 116. It may extend along axis 130 or parallel to this central axis. For example, in various embodiments, fuel inlet 102 may extend into or immediately upstream of venturi throat 116 for air 26 flow through mixing channel 114. In the above-described embodiment, providing a fuel inlet at or near the venturi throat 116 may advantageously provide an optimal pressure drop, in which case the air 26 flowing through the venturi geometry At the venturi throat 116, lower air pressures and higher velocities will be achieved compared to other parts of the mixing channel 114.

In embodiments that include a venturi shape, ignition source 120 may be positioned downstream of venturi throat 116. In some embodiments, ignition source 120 may be located downstream of mounting flange 122, for example as shown in Figure 5. In the above-described embodiment, ignition source 120 may be disposed within combustor 16, such as within head end 38. In another embodiment, the mounting flange 122 is positioned downstream of the ignition source 120, for example as illustrated in FIG. 6, so that the ignition source 120 is positioned when the igniter 100 is mounted on the end cover 36 of the combustor. ) may be positioned outside the combustor 16, for example outside the head end 38.

As illustrated in FIG. 5 , an embodiment of igniter 100 includes a mixing channel 112 defining a venturi shape without vortex 128 . As illustrated in FIG. 6 , an embodiment of igniter 100 includes a mixing channel 112 defining a venturi shape that combines with an ignition source 120 upstream of the mounting flange. As previously mentioned, features illustrated or described as part of one embodiment may be used in other embodiments to form still other embodiments. Other embodiments described above may include various combinations of the illustrated features. For example, a cylindrical mixing channel 112 as illustrated in FIG. 3 may be combined with an ignition source 120 downstream of the mounting flange 122 as illustrated in FIG. 5 . As another example, igniter 100 of Figure 5 may also include a swirler 138 as illustrated in Figures 3 and/or 6. Also as previously noted, each example is provided by way of illustration and not limitation, and the present disclosure is intended to cover such modifications and variations as fall within the scope of the appended claims and their equivalents.

7 and 8 illustrate another example embodiment of igniter 100. As illustrated in FIG. 7 , fuel conduit 108 may first be in fluid communication with fuel plenum 109 upstream of mixing plenum 110 . For example, the fuel conduit 108 may be in direct fluid communication with the fuel plenum 109 through a first fluid inlet 101 and a fuel inlet 102 as described above, in such embodiments a second fuel inlet. It can be. As illustrated in FIG. 7 , in some embodiments a fuel filter may be provided in the first fuel inlet 101 . Accordingly, the fuel conduit 108 may be in direct fluid communication with the fuel plenum 109 through the first fuel inlet 101 and in indirect fluid communication with the mixing plenum 110 through the second fuel inlet 102. It can be. For example, in the above-described embodiment, fuel 28 may flow from fuel plenum 109 through secondary fuel inlet 102 to mixing plenum 110 and air 26 may flow through air conduit 106. flows through the mixing plenum (110). Some embodiments also include a second fuel conduit 111 extending from the fuel plenum 108 to the combustor 16, such as through the end cover 36, to supply fuel 28 to the ignition spark. can do. For example, in some embodiments the ignition flame may be emitted from the ejector tube 126. Accordingly, the outlet 113 of the second fuel conduit 111 may be close to the outlet 127 of the ejector tube 126. As illustrated in FIG. 8 , second fuel conduit 111 may be proximate to, and in some embodiments may be abutting, ejector tube 126 . For example, the ignition source 120 may be positioned in a first portion, such as an upper portion, of the igniter 100, and the second fuel conduit 109 may be positioned in a second portion, such as a bottom portion, directly opposite the ignition source. can be set. As illustrated in FIG. 8 , in some embodiments the air inlet 104 is spaced apart from the ejector tube around the perimeter of the ejector tube 126 between the second fuel conduit 111 and the ignition source 120 (FIG. 7). It may be extended.

This written description discloses the technology, including its best mode, and provides examples to enable any person skilled in the art to practice the technology, including making and using any devices or systems and performing any integrated methods. Use . The patentable scope of the present technology is defined by the claims and may include other examples that occur to those skilled in the art. Such other examples are intended to fall within the scope of the claims if they have structural elements that do not differ substantially from the scope of the claims, or if they include equivalent structural elements that differ substantially from the scope of the claims.

Claims (20)

As a gas turbine,
compressor;
turbine;
a combustor disposed downstream from the compressor and upstream from the turbine; and
An igniter in operative communication with the combustor and configured to initiate combustion within the combustor.
Includes, and the igniter is
a mixing channel defining a venturi shape, the venturi shape comprising a converging section between an upstream end of the mixing channel and a venturi throat;
a fuel inlet in fluid communication with a mixing plenum positioned upstream of the mixing channel;
an air inlet in fluid communication with the mixing plenum; and
An ignition source in operative communication with the mixing channel and positioned downstream of the mixing plenum.
Including,
A gas turbine wherein the ignition source of the igniter is positioned downstream of the venturi throat. 2. The gas turbine of claim 1, wherein the igniter further includes a mounting flange configured to couple the igniter to the combustor, and the ignition source is located upstream of the mounting flange. delete 2. The gas turbine of claim 1, wherein the venturi shape of the mixing channel further includes a divergence section downstream of the venturi throat. 2. The gas turbine of claim 1, wherein the igniter further comprises a swirler downstream of the ignition source. 2. The gas turbine of claim 1, wherein the igniter is coupled to an end cover of the combustor and the central axis of the igniter is parallel to the central axis of the combustor. 2. The gas turbine of claim 1, wherein the igniter further comprises a fuel plenum upstream of the mixing plenum and a fuel conduit extending from the fuel plenum to the combustion chamber side in the combustor. 2. The gas turbine of claim 1, wherein the ignition source comprises a spark plug. As an ignitor for a combustor of a turbo machine,
a mounting flange configured to couple the igniter to the combustor;
a fuel inlet in fluid communication with a mixing plenum positioned upstream of the mixing channel;
an air inlet in fluid communication with the mixing plenum; and
an ignition source in operative communication with the mixing channel and positioned proximate the downstream end of the mixing channel and upstream of the mounting flange.
Including,
The mixing channel includes a convergence section between the upstream end of the mixing channel and the venturi throat,
A venturi throat is an igniter positioned upstream of an ignition source. delete delete ◈Claim 12 was abandoned upon payment of the setup registration fee.◈ 10. The igniter of claim 9, wherein the mixing channel further comprises a divergence section downstream of the venturi throat. delete ◈Claim 14 was abandoned upon payment of the setup registration fee.◈ 10. The igniter of claim 9 further comprising a swirler downstream of the ignition source. As an ignitor for a combustor of a turbo machine,
A mixing channel defining a plurality of distinct internal diameters, the plurality of distinct internal diameters comprising a first internal diameter in a first internal diameter portion and a minimum internal diameter in a throat portion downstream of the first internal diameter. ;
a fuel inlet in fluid communication with a mixing plenum positioned upstream of the mixing channel;
an air inlet in fluid communication with the mixing plenum; and
An ignition source in operative communication with the mixing channel and positioned downstream of the mixing plenum.
Including,
The ignition source is an igniter positioned downstream of the throat portion. delete ◈Claim 17 was abandoned upon payment of the setup registration fee.◈ 16. The igniter of claim 15, further comprising a mounting flange configured to couple the igniter to the combustor, wherein the ignition source is located upstream of the mounting flange. 16. The igniter of claim 15, wherein the plurality of distinct internal diameters in the mixing channel further include a second internal diameter in a second internal diameter downstream of the throat portion. ◈Claim 19 was abandoned upon payment of the setup registration fee.◈ 16. The igniter of claim 15 further comprising a swirler downstream of the ignition source. ◈Claim 20 was abandoned upon payment of the setup registration fee.◈ 16. The igniter of claim 15 further comprising a fuel plenum upstream of the mixing plenum and a fuel conduit extending from the fuel plenum.

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